Analysis of Composite Panels Subjected to Thermo-Mechanical LoadsSource: Journal of Aerospace Engineering:;1999:;Volume ( 012 ):;issue: 001DOI: 10.1061/(ASCE)0893-1321(1999)12:1(1)Publisher: American Society of Civil Engineers
Abstract: The results of a detailed study of the effect of cutout on the nonlinear response of curved unstiffened panels are presented. The panels are subjected to combined temperature gradient through-the-thickness combined with pressure loading and edge shortening or edge shear. The analysis is based on a first-order, shear-deformation, Sanders-Budiansky-type shell theory with the effects of large displacements, moderate rotations, transverse shear deformation, and laminated anisotropic material behavior included. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the panel. The nonlinear displacements, strain energy, principal strains, transverse shear stresses, transverse shear strain energy density, and their hierarchical sensitivity coefficients are evaluated. The hierarchical sensitivity coefficients measure the sensitivity of the nonlinear response to variations in the panel parameters, as well as in the material properties of the individual layers. Numerical results are presented for cylindrical panels and show the effects of variations in the loading and the size of the cutout on the global and local response quantities as well as their sensitivity to changes in the various panel, layer, and micromechanical parameters.
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contributor author | Ahmed K. Noor | |
contributor author | Jeanne M. Peters | |
date accessioned | 2017-05-08T21:15:58Z | |
date available | 2017-05-08T21:15:58Z | |
date copyright | January 1999 | |
date issued | 1999 | |
identifier other | %28asce%290893-1321%281999%2912%3A1%281%29.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/44888 | |
description abstract | The results of a detailed study of the effect of cutout on the nonlinear response of curved unstiffened panels are presented. The panels are subjected to combined temperature gradient through-the-thickness combined with pressure loading and edge shortening or edge shear. The analysis is based on a first-order, shear-deformation, Sanders-Budiansky-type shell theory with the effects of large displacements, moderate rotations, transverse shear deformation, and laminated anisotropic material behavior included. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the panel. The nonlinear displacements, strain energy, principal strains, transverse shear stresses, transverse shear strain energy density, and their hierarchical sensitivity coefficients are evaluated. The hierarchical sensitivity coefficients measure the sensitivity of the nonlinear response to variations in the panel parameters, as well as in the material properties of the individual layers. Numerical results are presented for cylindrical panels and show the effects of variations in the loading and the size of the cutout on the global and local response quantities as well as their sensitivity to changes in the various panel, layer, and micromechanical parameters. | |
publisher | American Society of Civil Engineers | |
title | Analysis of Composite Panels Subjected to Thermo-Mechanical Loads | |
type | Journal Paper | |
journal volume | 12 | |
journal issue | 1 | |
journal title | Journal of Aerospace Engineering | |
identifier doi | 10.1061/(ASCE)0893-1321(1999)12:1(1) | |
tree | Journal of Aerospace Engineering:;1999:;Volume ( 012 ):;issue: 001 | |
contenttype | Fulltext |